1. Preliminary Rocket Design Objectives: 1. Comprehend a preliminary sizing example for a rocket 2. Explain basic trade-offs in rocket design

2. Design Process Define Mission Requirements Define Mission Requirements Delta V, Payload Mass, Orbital Altitude Delta V, Payload Mass, Orbital Altitude Develop Criteria for Evaluating and Selecting Systems Develop Criteria for Evaluating and Selecting Systems Cost, environmental impacts, development time (schedule), risk, -illities (produce-ability, transportability, storability, testability) Cost, environmental impacts, development time (schedule), risk, -illities (produce-ability, transportability, storability, testability) Develop Alternative Mission Concepts Develop Alternative Mission Concepts 2-3 alternatives per mission 2-3 alternatives per mission

3. Design Process Define the Vehicle System and Identify Potential Technologies Define the Vehicle System and Identify Potential Technologies Develop a Preliminary Design Develop a Preliminary Design Assess the Design Assess the Design Compare the Designs and Chose Best Options Compare the Designs and Chose Best Options ITERATE ITERATE

4. AK-5 Design Scenario We want to take a basic set of requirements for a small sounding rocket and see how we can determine the initial sizing for the rocket. Let’s start with these requirements: We want to take a basic set of requirements for a small sounding rocket and see how we can determine the initial sizing for the rocket. Let’s start with these requirements: Payload mass = 5 kg. This is to accommodate a small, high- altitude atmospheric science experiment. Payload mass = 5 kg. This is to accommodate a small, high- altitude atmospheric science experiment. Maximum altitude = 100 km. This is to provide a sufficient time at altitude for the experiment to collect data. Maximum altitude = 100 km. This is to provide a sufficient time at altitude for the experiment to collect data. The rocket must use liquid propellants and they must be as non- toxic as possible (this is a student program). The rocket must use liquid propellants and they must be as non- toxic as possible (this is a student program). To guarantee the rocket will be aerodynamically stable at liftoff, the minimum thrust to weight ratio is 5. To guarantee the rocket will be aerodynamically stable at liftoff, the minimum thrust to weight ratio is 5. The design thrust for the rocket is 500 lbf. The design thrust for the rocket is 500 lbf. Now, we can start determining ΔV, Isp, and f-inert required for this new rocket. Now, we can start determining ΔV, Isp, and f-inert required for this new rocket.

5. D-K Equation D-K Equation

6. D-K Chart 0.04 0.12 0.2 0.28 0.36